Numerical Analysis and Experimental Techniques for Static Aeroelastic Divergence of Wing
Aeroelastic divergence analysis of a stable wing structure was performed using a coupled aerodynamic/structural method and validated using wind tunnel tests. To ensure the accuracy of numerical analysis, CFD method was used for aerodynamic force calculation and finite element method was used for str...
| Główni autorzy: | , , |
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| Format: | Artykuł |
| Język: | zho |
| Wydane: |
China Astronautic Publishing CO., LTD. ; Editorial Office of Physics of Gases
2023-11-01
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| Seria: | 气体物理 |
| Hasła przedmiotowe: | |
| Dostęp online: | http://qtwl.xml-journal.net/cn/article/doi/10.19527/j.cnki.2096-1642.1087 |
| _version_ | 1827382777093292032 |
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| author | Kai LIU Kai-hua YUAN Hai-tao TIAN |
| author_facet | Kai LIU Kai-hua YUAN Hai-tao TIAN |
| author_sort | Kai LIU |
| collection | DOAJ |
| description | Aeroelastic divergence analysis of a stable wing structure was performed using a coupled aerodynamic/structural method and validated using wind tunnel tests. To ensure the accuracy of numerical analysis, CFD method was used for aerodynamic force calculation and finite element method was used for structural deformation calculation. The wind tunnel test used a sidewall insertion mechanism for support and measured the static aeroelastic divergence characteristics through strain measurement and high-speed photography. The stable wing model was used as the research object for studying the static aeroelastic divergence characteristics in supersonic state. The results of numerical calculation and wind tunnel test showed that the CFD/CSD coupling method can accurately predict the static aeroelastic divergence boundary. Static aeroelastic divergence presents an explosive form of destruction. The static aeroelastic unstable structure first suffers from elastic loading exceeding the structural strength limit and the damage occurs with the dynamic pressure not reaching the divergence boundary. Accurate prediction of the static aeroelastic divergence boundary of the aircraft is necessary for aircraft structural design. |
| first_indexed | 2024-03-08T14:26:22Z |
| format | Article |
| id | doaj.art-a3d02f1c5f8e4041abd3fcfbb30a2f3f |
| institution | Directory Open Access Journal |
| issn | 2096-1642 |
| language | zho |
| last_indexed | 2024-03-08T14:26:22Z |
| publishDate | 2023-11-01 |
| publisher | China Astronautic Publishing CO., LTD. ; Editorial Office of Physics of Gases |
| record_format | Article |
| series | 气体物理 |
| spelling | doaj.art-a3d02f1c5f8e4041abd3fcfbb30a2f3f2024-01-13T01:09:38ZzhoChina Astronautic Publishing CO., LTD. ; Editorial Office of Physics of Gases气体物理2096-16422023-11-0186758010.19527/j.cnki.2096-1642.1087qtwl-8-6-75Numerical Analysis and Experimental Techniques for Static Aeroelastic Divergence of WingKai LIU0Kai-hua YUAN1Hai-tao TIAN2Beijing Institute of Mechanical and Electrical Engineering, Beijing 100074, ChinaBeijing Institute of Mechanical and Electrical Engineering, Beijing 100074, ChinaBeijing Institute of Mechanical and Electrical Engineering, Beijing 100074, ChinaAeroelastic divergence analysis of a stable wing structure was performed using a coupled aerodynamic/structural method and validated using wind tunnel tests. To ensure the accuracy of numerical analysis, CFD method was used for aerodynamic force calculation and finite element method was used for structural deformation calculation. The wind tunnel test used a sidewall insertion mechanism for support and measured the static aeroelastic divergence characteristics through strain measurement and high-speed photography. The stable wing model was used as the research object for studying the static aeroelastic divergence characteristics in supersonic state. The results of numerical calculation and wind tunnel test showed that the CFD/CSD coupling method can accurately predict the static aeroelastic divergence boundary. Static aeroelastic divergence presents an explosive form of destruction. The static aeroelastic unstable structure first suffers from elastic loading exceeding the structural strength limit and the damage occurs with the dynamic pressure not reaching the divergence boundary. Accurate prediction of the static aeroelastic divergence boundary of the aircraft is necessary for aircraft structural design.http://qtwl.xml-journal.net/cn/article/doi/10.19527/j.cnki.2096-1642.1087aeroelasticitydivergencenumerical simulationwind tunnel test |
| spellingShingle | Kai LIU Kai-hua YUAN Hai-tao TIAN Numerical Analysis and Experimental Techniques for Static Aeroelastic Divergence of Wing 气体物理 aeroelasticity divergence numerical simulation wind tunnel test |
| title | Numerical Analysis and Experimental Techniques for Static Aeroelastic Divergence of Wing |
| title_full | Numerical Analysis and Experimental Techniques for Static Aeroelastic Divergence of Wing |
| title_fullStr | Numerical Analysis and Experimental Techniques for Static Aeroelastic Divergence of Wing |
| title_full_unstemmed | Numerical Analysis and Experimental Techniques for Static Aeroelastic Divergence of Wing |
| title_short | Numerical Analysis and Experimental Techniques for Static Aeroelastic Divergence of Wing |
| title_sort | numerical analysis and experimental techniques for static aeroelastic divergence of wing |
| topic | aeroelasticity divergence numerical simulation wind tunnel test |
| url | http://qtwl.xml-journal.net/cn/article/doi/10.19527/j.cnki.2096-1642.1087 |
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